Turbomachinery Blade Modal Analysis Using Contact Elements

2004-01-3141

11/02/2004

Event
World Aviation Congress & Exposition
Authors Abstract
Content
This paper presents a new methodology for analytically evaluating the natural frequencies and mode shape of a turbomachinery blade in an environment where friction phenomenon occurs. The blades analyzed in this study are unshrouded and located in the high-pressure turbine found in turbofan engines, and in the compressor turbine found in turboprop engines. The goal of this method is to correctly predict the modal parameters of the blade in order to determine whether there will be any resonance in the running range of the turbomachinery, and to more accurately predict the stresses at the blade-disc interface. This study was performed using ANSYS® contact elements. After comparison, the analytical results were found to agree with the experimental results. A convergence study was also performed, and it was found that only the friction coefficient and the surface contact stiffness had a considerable effect on the natural frequencies and mode shape convergence.
Meta TagsDetails
DOI
https://doi.org/10.4271/2004-01-3141
Pages
8
Citation
Guerra, M., Thomas, M., and St-Georges, L., "Turbomachinery Blade Modal Analysis Using Contact Elements," SAE Technical Paper 2004-01-3141, 2004, https://doi.org/10.4271/2004-01-3141.
Additional Details
Publisher
Published
Nov 2, 2004
Product Code
2004-01-3141
Content Type
Technical Paper
Language
English